Rigid spacecraft attitude tracking using finite time sliding mode control

In this work, using the finite time sliding mode control, the design of attitude tracking control of a rigid spacecraft has been discussed. The proposed control law has been designed by using the novel fast terminal sliding mode surface with a reaching law. The proposed control law, avoids the singularity possibility, and offers the faster convergence speed in the reaching phase and in the sliding phase. In addition, the applied control input is continuous in nature. The finite time stability has been proved using the Lyapunov theory. In last, to show the effectiveness of the proposed control method, simulations have been conducted under the conditions of mass inertia uncertainty and external disturbances, and the results, in comparison with the existing methods have been demonstrated.